WO2008122751A2 - A computer and a method of modelling a woven composite material - Google Patents

A computer and a method of modelling a woven composite material Download PDF

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Publication number
WO2008122751A2
WO2008122751A2 PCT/GB2008/000713 GB2008000713W WO2008122751A2 WO 2008122751 A2 WO2008122751 A2 WO 2008122751A2 GB 2008000713 W GB2008000713 W GB 2008000713W WO 2008122751 A2 WO2008122751 A2 WO 2008122751A2
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WO
WIPO (PCT)
Prior art keywords
woven fabric
domain
tow
fabric composite
modelling
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PCT/GB2008/000713
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French (fr)
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WO2008122751A3 (en
Inventor
Wen-Guang Jiang
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Rolls-Royce Plc
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Publication of WO2008122751A2 publication Critical patent/WO2008122751A2/en
Publication of WO2008122751A3 publication Critical patent/WO2008122751A3/en

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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/12—Cloth
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/26—Composites

Definitions

  • the present invention relates to modelling of woven fabric composites, in particular to modelling of woven fabric composites in a finite element analysis method and a process for stress analysis of woven fabric composites for implementation in a finite element analysis method.
  • Woven fabric composites comprise woven tows, or woven fibres, in a matrix material.
  • Woven fabric composites provide various attractive properties such as light weight, low fabrication costs, ease of handing and high adaptability when compared to tape laminates and more traditional engineering materials. With these cost and performance advantages, woven fabric composites have received increased attention and popularity in . many structural applications in recent years.
  • the prior art methods of modelling woven fabric composites are limited by the time taken to prepare detailed models, or are limited by the level of accuracy obtainable due to simplifications made.
  • the two main approaches taken are the previously mentioned unit cell approach, which explicitly models the tows and the matrix material with a congruent mesh and homogenisation which uses effective properties "smeared" between the tows and matrix material.
  • the unit cell approach results in very- large models of the woven fabric composite, which are only of a small piece of the whole woven fabric composite and are not tolerant to interpenetration among the modelled tow geometries.
  • the binary model approach gives much simpler models, which are quick to run, but are far less accurate due to losing the tow/matrix material interface detail.
  • Another approach combines the homogenised approach with the detail of the unit cell approach by embedding 2D beam elements in an effective medium to represent the tows.
  • the present invention seeks to provide a novel method of modelling woven fabric composites, which reduces, preferably overcomes, the above-mentioned problems .
  • the present invention provides a method of modelling a woven fabric composite comprising producing at least two domains, producing a tow domain to represent the tows of the woven fabric composite, producing a global domain to represent the matrix material of the woven fabric material, super-positioning the tow domain and the global domain, applying the material behaviour configurations to the tow domain and to the global domain and providing coupling relationships between the two domains.
  • the method comprises modelling the woven fabric composite using a finite element analysis technique.
  • the method comprises coupling the tow finite element mesh to the global finite element mesh.
  • the method comprises modelling the tow domain as solid elements and the global domain as solid elements .
  • the method comprises using the actual matrix material properties for the global domain.
  • the method comprises using the difference between the actual tow material properties and the actual matrix material properties for the tow domain.
  • the tows of the woven fabric composite comprise a 3D arrangement of tows.
  • the woven fabric composite comprises a gas turbine engine component.
  • the gas turbine engine component comprises a fan blade, a compressor blade, a casing, a compressor rotor or a turbine rotor.
  • a computer system programmed to model a woven fabric composite comprising means to produce a tow domain to represent the tows of the woven fabric composite, means to produce a global domain to represent the matrix material of the woven fabric material, means to super-positioning the tow domain and the global domain, means to apply the material behaviour configurations to the tow domain and to the global domain and means to provide coupling relationships between the two domains.
  • the computer system comprises a means for a finite element analysis.
  • the computer system comprises means to couple the tow finite element mesh to the global finite element mesh.
  • the computer system comprises means to model the tow domain as solid elements and the global domain as solid elements.
  • the means to apply the material behaviour configurations comprises means to use the actual matrix material properties for the global domain.
  • the means to apply the material behaviour configurations comprises means to use the difference between the actual tow material properties and the actual matrix material properties.
  • Figure 1 shows a typical finite element mesh for a unit cell of a plain weave composite material used in a model according to the present invention.
  • Figure 2 shows stress analysis results under a tensile load for a unit cell of a plain weave composite material used in a model according to the present invention.
  • the present invention instead of modelling the tows and the likely degenerated resin pockets explicitly, the present invention creates at least two domains, a tow domain and a global domain, which are both non-degenerated separately. Both the tow domain and the global domain are modelled using solid elements and the final result is simply the superposition of the two domains.
  • the implementation of the present invention requires two essential technical strategies. The first is the derivation of the correct material behaviour configurations of the two domains. The second is the establishment of coupling relationships between the two domains.
  • the actual matrix material- property is used for the elements of the global domain and the elements in the tow domains use a modified mechanical model, i.e. the constitutive stiffness matrix used takes the difference ' between the actual tow material and that of the matrix material.
  • the independent tow finite element (FE) meshes need to be connected into the global finite element (FE) mesh and this is implemented by the coupling technique. This ensures that the two phases of the superimposed materials in the tow space have an equivalent mechanical property of the actual tows, and the remaining matrix material domain has the unchanged matrix material property.
  • FE finite element
  • each tow is independently discretised using 8-noded solid elements by simply dragging the cross-sectional area along the centre line of the tow and each element has edges parallel to the centre line of the tow, which can ' be conveniently used for material orientation.
  • the global space can be easily meshed using solid elements without the need of considering the very complex material distributions within the domain.
  • Thirdly the actual matrix material space is not modelled explicitly, whilst the traditional finite element (FE) analysis requires significant computational resources to cope with this.
  • FE finite element
  • FIG. 1 An example of a finite element mesh for a unit cell of a plain weave composite material is shown in Figure 1.
  • Figure 1 (a) shows the tow mesh for a typical finite element mesh for a unit cell of a plain weave composite material.
  • Figure 1 (b) shows the global mesh for a typical finite element mesh for a unit cell of the plain weave composite material- and
  • Figure 1 (c) shows the superimposed mesh of the tow mesh and the global mesh of the plain weave composite material according to the present invention.
  • Figure 2 shows the global displacement distribution in the tensile direction.
  • Figure 2 (b) shows the stress in the tow direction in the warp tows and
  • Figure 2 (c) shows the stress in the tow direction in the " weft tows .
  • the model according to the present invention has been validated against standard finite element (FE) methods.
  • the present invention uses domain superposition techniques and embeds solid elements to represent the tows, a tow mesh, in a global mesh, which represents the matrix material. Where the two meshes overlap the material properties are adjusted so that the matrix material is
  • the present invention retains the detail of the tow geometry whilst at the same time coping with the interpenetrating tows and this results in greatly reduced model size, which may be applied to much larger structures than the unit cell approach.
  • the present invention may be used for any woven material in which tows, fibres, and matrix material are combined to form a woven composite material.
  • the present invention is capable of handling highly complex internal architecture, structure, such as that provided in 3D woven composite materials due to its ability to cope with interpenetrating tows and to produce models of reduced size, when compared to the unit cell approach and has increased accuracy when compared to the homogenised material approach.
  • the present invention includes a computer system arranged to perform this method.
  • the present invention is applicable for use with polymer, or resin, matrix woven fabric composites, ceramic matrix woven fabric composites or metal matrix woven fabric composites.
  • the present invention is applicable for modelling gas turbine engine woven fabric composite components, e.g. fan blades, compressor blades, compressor vanes, casings, compressor rotors, turbine rotors, turbine blades, turbine vanes etc. It may also be suitable for modelling woven fabric composite components for other engines, machines or structures .
  • the present invention is applicable for use with woven fabric composites with 2D arrangements of tows, fibres, and/or for use with woven fabric composites with 3D arrangements of tows, fibres.
  • the model of the woven fabric composite according to the present invention may be used in the prediction of the mechanical behaviour of woven fabric composite and to provide indication of the resulting stresses for applied strains.
  • the model of the woven fabric composite is provided in a finite element analysis method and the mechanical behaviour of the woven fabric composite is provided by stress analysis of the finite element analysis model of the woven fabric composite.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • Geometry (AREA)
  • General Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Reinforced Plastic Materials (AREA)
  • Woven Fabrics (AREA)

Abstract

A method of modelling a woven fabric composite comprising producing a tow domain to represent the tows of the woven fabric composite, producing a global domain to represent the matrix material of the woven fabric material, super-positioning the tow domain and the global domain, applying the material behaviour configurations to the tow domain and to the global domain and providing coupling relationships between the two domains.

Description

A COMPUTER AND A METHOD OF MODELLING A WOVEN COMPOSITE
MATERIAL
The present invention relates to modelling of woven fabric composites, in particular to modelling of woven fabric composites in a finite element analysis method and a process for stress analysis of woven fabric composites for implementation in a finite element analysis method.
Woven fabric composites comprise woven tows, or woven fibres, in a matrix material. Woven fabric composites provide various attractive properties such as light weight, low fabrication costs, ease of handing and high adaptability when compared to tape laminates and more traditional engineering materials. With these cost and performance advantages, woven fabric composites have received increased attention and popularity in . many structural applications in recent years.
A paper by J.J. Crookston, A. C. Long, I. A. Jones - A summary review of mechanical properties prediction methods for textile reinforced polymer composites, Proc. ImechE, Part L: J. Materials: Design and Applications; 219, 91-109,
2005 shows that finite element (FE) and theoretical analysis methods are one of the tools available for studying the mechanical properties of woven fabric composites. The micro-structure of woven fabric composites is complex in nature and the parameters controlling the mechanical properties of woven fabric composites are numerous, therefore it is difficult to model woven fabric composites in detail using the traditional finite element
(FE) methods. Various finite element techniques and assumptions have been proposed for simplifying the analysis .
Most of the models for woven fabric composites are based on the definition of unit cell geometry and include the major architectural parameters in predicting the mechanical properties of the woven fabric composite. One of the fundamental difficulties faced in modelling the detailed unit cell of a woven fabric composite using solid elements is to build geometry free from interpenetration at tow crossovers. Furthermore, a very fine finite element (FE) mesh is required to deal with some "not^quite- relevant" details, i.e. the degenerated volumes of the resin pockets. This can lead t'o a very large finite element (FE) model exceeding a million degrees of freedom to model only a unit cell, which is only a very small part of the woven fabric composite structure.
A paper by B.N. Cox, W. C. Carter, N. A. Fleck - A binary model of textile composites I. Formulation, ACTA Metallurgica et Materialia, 42 (10), 3463-3479, 1994 developed a finite element (FE) model, known as the λbinary model', for simulating woven textile composites. In this model, axial properties of tows were represented by two- noded line elements possessing axial rigidity, while the transverse stiffness, shear stiffness, and Poisson' s effect of the composite were represented by an eight-node solid ^effective medium' element. Due to the simplified assumptions, a complex parameter calibration is needed to yield good correlation, which could still be mesh size dependent. Another significant simplification is that the detailed tow geometric features are omitted, making the actual stress calculation process quite complex.
Thus, the prior art methods of modelling woven fabric composites are limited by the time taken to prepare detailed models, or are limited by the level of accuracy obtainable due to simplifications made. The two main approaches taken are the previously mentioned unit cell approach, which explicitly models the tows and the matrix material with a congruent mesh and homogenisation which uses effective properties "smeared" between the tows and matrix material. The unit cell approach results in very- large models of the woven fabric composite, which are only of a small piece of the whole woven fabric composite and are not tolerant to interpenetration among the modelled tow geometries. The binary model approach gives much simpler models, which are quick to run, but are far less accurate due to losing the tow/matrix material interface detail. Another approach combines the homogenised approach with the detail of the unit cell approach by embedding 2D beam elements in an effective medium to represent the tows.
Accordingly the present invention seeks to provide a novel method of modelling woven fabric composites, which reduces, preferably overcomes, the above-mentioned problems . Accordingly the present invention provides a method of modelling a woven fabric composite comprising producing at least two domains, producing a tow domain to represent the tows of the woven fabric composite, producing a global domain to represent the matrix material of the woven fabric material, super-positioning the tow domain and the global domain, applying the material behaviour configurations to the tow domain and to the global domain and providing coupling relationships between the two domains.
Preferably the method comprises modelling the woven fabric composite using a finite element analysis technique.
Preferably the method comprises coupling the tow finite element mesh to the global finite element mesh.
Preferably the method comprises modelling the tow domain as solid elements and the global domain as solid elements .
Preferably the method comprises using the actual matrix material properties for the global domain. Preferably the method comprises using the difference between the actual tow material properties and the actual matrix material properties for the tow domain.
Preferably the tows of the woven fabric composite comprise a 3D arrangement of tows.
Preferably the woven fabric composite comprises a gas turbine engine component.
Preferably the gas turbine engine component comprises a fan blade, a compressor blade, a casing, a compressor rotor or a turbine rotor.
A computer system programmed to model a woven fabric composite comprising means to produce a tow domain to represent the tows of the woven fabric composite, means to produce a global domain to represent the matrix material of the woven fabric material, means to super-positioning the tow domain and the global domain, means to apply the material behaviour configurations to the tow domain and to the global domain and means to provide coupling relationships between the two domains. Preferably the computer system comprises a means for a finite element analysis.
Preferably the computer system comprises means to couple the tow finite element mesh to the global finite element mesh. Preferably the computer system comprises means to model the tow domain as solid elements and the global domain as solid elements.
Preferably the means to apply the material behaviour configurations comprises means to use the actual matrix material properties for the global domain.
Preferably the means to apply the material behaviour configurations comprises means to use the difference between the actual tow material properties and the actual matrix material properties. The present invention will be more fully described by way of example with reference to the accompanying drawings in which :-
Figure 1 shows a typical finite element mesh for a unit cell of a plain weave composite material used in a model according to the present invention.
Figure 2 shows stress analysis results under a tensile load for a unit cell of a plain weave composite material used in a model according to the present invention. In the present invention instead of modelling the tows and the likely degenerated resin pockets explicitly, the present invention creates at least two domains, a tow domain and a global domain, which are both non-degenerated separately. Both the tow domain and the global domain are modelled using solid elements and the final result is simply the superposition of the two domains. The implementation of the present invention requires two essential technical strategies. The first is the derivation of the correct material behaviour configurations of the two domains. The second is the establishment of coupling relationships between the two domains. For the material models, the actual matrix material- property is used for the elements of the global domain and the elements in the tow domains use a modified mechanical model, i.e. the constitutive stiffness matrix used takes the difference' between the actual tow material and that of the matrix material. The independent tow finite element (FE) meshes need to be connected into the global finite element (FE) mesh and this is implemented by the coupling technique. This ensures that the two phases of the superimposed materials in the tow space have an equivalent mechanical property of the actual tows, and the remaining matrix material domain has the unchanged matrix material property. Compared with conventional finite element (FE) models of woven fabric composites, the present invention has several^ advantages. Firstly each tow is independently discretised using 8-noded solid elements by simply dragging the cross-sectional area along the centre line of the tow and each element has edges parallel to the centre line of the tow, which can ' be conveniently used for material orientation. Secondly the global space can be easily meshed using solid elements without the need of considering the very complex material distributions within the domain. Thirdly the actual matrix material space is not modelled explicitly, whilst the traditional finite element (FE) analysis requires significant computational resources to cope with this. Fourthly defects in the geometric model, e.g. the difficult-to-avoid interpenetration at tow crossovers from the creation of the geometric models, can be tolerated in the present invention. Fifthly the model size may be reduced.
An example of a finite element mesh for a unit cell of a plain weave composite material is shown in Figure 1. Figure 1 (a) shows the tow mesh for a typical finite element mesh for a unit cell of a plain weave composite material. Figure 1 (b) shows the global mesh for a typical finite element mesh for a unit cell of the plain weave composite material- and Figure 1 (c) shows the superimposed mesh of the tow mesh and the global mesh of the plain weave composite material according to the present invention.
Analysis results under a unit tensile load are given in Figure 2. Figure 2 (a) shows the global displacement distribution in the tensile direction. Figure 2 (b) shows the stress in the tow direction in the warp tows and Figure 2 (c) shows the stress in the tow direction in the" weft tows . The model according to the present invention has been validated against standard finite element (FE) methods.
Thus the present invention uses domain superposition techniques and embeds solid elements to represent the tows, a tow mesh, in a global mesh, which represents the matrix material. Where the two meshes overlap the material properties are adjusted so that the matrix material is
• subtracted from the tow material. The two meshes are then connected via a set of constrain equations, which couples the two meshes in the analysis.
The present invention retains the detail of the tow geometry whilst at the same time coping with the interpenetrating tows and this results in greatly reduced model size, which may be applied to much larger structures than the unit cell approach. The present invention may be used for any woven material in which tows, fibres, and matrix material are combined to form a woven composite material. The present invention is capable of handling highly complex internal architecture, structure, such as that provided in 3D woven composite materials due to its ability to cope with interpenetrating tows and to produce models of reduced size, when compared to the unit cell approach and has increased accuracy when compared to the homogenised material approach. The present invention includes a computer system arranged to perform this method.
The present invention is applicable for use with polymer, or resin, matrix woven fabric composites, ceramic matrix woven fabric composites or metal matrix woven fabric composites.
The present invention is applicable for modelling gas turbine engine woven fabric composite components, e.g. fan blades, compressor blades, compressor vanes, casings, compressor rotors, turbine rotors, turbine blades, turbine vanes etc. It may also be suitable for modelling woven fabric composite components for other engines, machines or structures .
The present invention is applicable for use with woven fabric composites with 2D arrangements of tows, fibres, and/or for use with woven fabric composites with 3D arrangements of tows, fibres.
The model of the woven fabric composite according to the present invention may be used in the prediction of the mechanical behaviour of woven fabric composite and to provide indication of the resulting stresses for applied strains. In particular the model of the woven fabric composite is provided in a finite element analysis method and the mechanical behaviour of the woven fabric composite is provided by stress analysis of the finite element analysis model of the woven fabric composite.
Although the present invention has been described with reference to the use of two domains, it may be applicable to more than two domains.

Claims

Claims : -
1. A method of modelling a woven fabric composite comprising producing at least two domains, producing a tow, domain to represent the tows of the woven fabric composite, producing a global domain to represent the matrix material of the woven fabric composite, super-positioning the tow domain and the global domain, applying the material behaviour configurations to the tow domain and to the global domain and providing coupling relationships between the two domains.
2. A method of modelling a woven fabric composite as claimed in claim 1 comprising modelling the woven fabric composite using a finite element analysis technique.
3. A method of modelling a woven fabric composite as claimed in claim 2 comprising coupling the tow finite element mesh to the global finite element mesh.
4. A method of modelling a woven fabric composite as claimed in any of claims 1 to 3 comprising modelling the tow domain as solid elements and the global domain as solid elements.
5. A method of modelling a woven fabric composite as claimed in any of claims 1 to 4 comprising using the actual matrix material properties for the global domain.
6. A method of modelling a woven fabric composite as claimed in any of claims 1 to 5 comprising using the difference between the actual tow material properties and the actual matrix material properties for the tow domain.
7. A' method of modelling a woven fabric composite as claimed in any of claims 1 to 6 wherein the tows of the woven fabric composite comprises a 3D arrangement of tows.
8. A method of modelling a woven fabric composite as claimed in any of claims 1 to 7 wherein the woven fabric composite comprises a gas turbine engine component.
9. A method of modelling a woven fabric composite as claimed in claim 8 wherein the gas turbine engine component comprises a fan blade, a compressor blade, a casing, a compressor rotor or a turbine rotor.
10. A computer system programmed to model a woven fabric composite comprising means to produce a tow domain to represent the tows of the woven fabric composite, means to produce a global domain to represent the matrix material of the woven fabric composite, means to super-positioning the tow domain and the global domain, means to apply the material behaviour configurations to the tow domain and to the global domain and means to provide coupling relationships between the two domains.
11. A computer system as claimed in claim 10 comprising a means for a finite element analysis.
12. A computer system as claimed in claim 11 comprising means to couple the tow finite element mesh to the global finite element mesh.
13. A computer system as claimed in any of claims 10 to 12 comprising means to model the tow domain as solid elements and the global domain as solid elements.
14. A computer system as claimed in any of claims 10 to 13 wherein the means to apply the material behaviour configurations comprises means to use the actual matrix material properties for the global domain.
15. A computer system as claimed in any of claims 10 to 14 wherein the means to apply the material behaviour configurations comprises means to use the difference between the actual tow material properties and the actual matrix material properties.
PCT/GB2008/000713 2007-04-04 2008-03-04 A computer and a method of modelling a woven composite material WO2008122751A2 (en)

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CN107273646A (en) * 2017-08-04 2017-10-20 中国航空工业集团公司西安飞机设计研究所 Metal and bolt connection Calculation Methods for Internal Force in multiple material mixed structure under temperature
WO2019182964A1 (en) * 2018-03-17 2019-09-26 Drexel University Topology optimization for modeling and prediction of complex fabric structures and properties
US10677259B2 (en) 2016-05-06 2020-06-09 General Electric Company Apparatus and system for composite fan blade with fused metal lead edge
US10746045B2 (en) 2018-10-16 2020-08-18 General Electric Company Frangible gas turbine engine airfoil including a retaining member
US10760428B2 (en) 2018-10-16 2020-09-01 General Electric Company Frangible gas turbine engine airfoil
US10837286B2 (en) 2018-10-16 2020-11-17 General Electric Company Frangible gas turbine engine airfoil with chord reduction
US11111815B2 (en) 2018-10-16 2021-09-07 General Electric Company Frangible gas turbine engine airfoil with fusion cavities
US11149558B2 (en) 2018-10-16 2021-10-19 General Electric Company Frangible gas turbine engine airfoil with layup change
CN113868931A (en) * 2021-12-03 2021-12-31 季华实验室 Composite finite element modeling method and system and storage medium
US11434781B2 (en) 2018-10-16 2022-09-06 General Electric Company Frangible gas turbine engine airfoil including an internal cavity
US11668317B2 (en) 2021-07-09 2023-06-06 General Electric Company Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy
US11674399B2 (en) 2021-07-07 2023-06-13 General Electric Company Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy
US11859321B2 (en) 2021-03-31 2024-01-02 Drexel University Modular tool for design of self-folding knit fabrics

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9777593B2 (en) 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
US10677259B2 (en) 2016-05-06 2020-06-09 General Electric Company Apparatus and system for composite fan blade with fused metal lead edge
CN107273646A (en) * 2017-08-04 2017-10-20 中国航空工业集团公司西安飞机设计研究所 Metal and bolt connection Calculation Methods for Internal Force in multiple material mixed structure under temperature
WO2019182964A1 (en) * 2018-03-17 2019-09-26 Drexel University Topology optimization for modeling and prediction of complex fabric structures and properties
US11761128B2 (en) 2018-03-17 2023-09-19 Drexel University Topology optimization for modeling and prediction of complex fabric structures and properties
US11149558B2 (en) 2018-10-16 2021-10-19 General Electric Company Frangible gas turbine engine airfoil with layup change
US10837286B2 (en) 2018-10-16 2020-11-17 General Electric Company Frangible gas turbine engine airfoil with chord reduction
US11111815B2 (en) 2018-10-16 2021-09-07 General Electric Company Frangible gas turbine engine airfoil with fusion cavities
US10760428B2 (en) 2018-10-16 2020-09-01 General Electric Company Frangible gas turbine engine airfoil
US11434781B2 (en) 2018-10-16 2022-09-06 General Electric Company Frangible gas turbine engine airfoil including an internal cavity
US10746045B2 (en) 2018-10-16 2020-08-18 General Electric Company Frangible gas turbine engine airfoil including a retaining member
US11859321B2 (en) 2021-03-31 2024-01-02 Drexel University Modular tool for design of self-folding knit fabrics
US11674399B2 (en) 2021-07-07 2023-06-13 General Electric Company Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy
US11668317B2 (en) 2021-07-09 2023-06-06 General Electric Company Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy
CN113868931A (en) * 2021-12-03 2021-12-31 季华实验室 Composite finite element modeling method and system and storage medium
CN113868931B (en) * 2021-12-03 2022-03-25 季华实验室 Composite finite element modeling method and system and storage medium

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